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    Propeller phase control apparatus
    11.
    发明公开
    Propeller phase control apparatus 失效
    Vorrichtung zur Kontrolle der Propellerphase。

    公开(公告)号：EP0322343A2

    公开(公告)日：1989-06-28

    申请号：EP88630228.0

    申请日：1988-12-14

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Martin, Anthony Newman

    IPC分类号： B64C11/50 ,  B64D31/12

    CPC分类号： B64C11/50 ,  B64D31/12 ,  Y02T50/66

    摘要： Propeller phase control apparatus for use on multi-engine aircraft having, for each engine (12,14), an electronic engine control (EEC) (21,22) for providing an EEC command speed and phase (S/P) signal to control propeller phase and shaft speed, and a speed and phase control (SPC) (23,24) for regulating the propeller's blade pitch angle to adjust the shaft speed thereof in dependence on the EEC command S/P signal value, includes: a SYNCHROPHASER Reference Unit (SRU) (18) having a signal processor with signal memory, the memory including stored signals definitive of a speed and phase algorithm, the signal processor calculating a common SRU command S/P signal value for all SPCs in accordance with the algorithm and in dependence on the sensed values of selected flight data indicative of engine performance, and further includes an electronic switch (19,20) for each SPC, for selecting either the SRU command S/P signal or the engine's EEC command S/P signal for presentation to the SPC.

    摘要翻译： 用于多发机飞行器的螺旋桨相位控制装置，对于每个发动机（12,14），具有用于提供EEC命令速度和相位（S / P）信号以控制的电子发动机控制（EEC）（21,22） 螺旋桨相位和轴速度，以及用于根据EEC命令S / P信号值调节螺旋桨叶片桨距角以调节其轴速度的速度和相位控制（SP）（23,24），包括：SYNCHROPHASER参考 具有信号处理器的单元（SRU）（18）具有信号存储器，所述存储器包括存储的速度和相位算法确定的信号，所述信号处理器根据所述算法计算所有SPC的公共SRU命令S / P信号值，以及 依赖于指示发动机性能的所选飞行数据的感测值，并且还包括用于每个SPC的电子开关（19,20），用于选择SRU命令S / P信号或发动机的EEC命令S / P信号，用于 向SPC演示。

    AIRCRAFT ROTOR ASSEMBLY WITH PLURAL ROTORS
    16.
    发明公开
    AIRCRAFT ROTOR ASSEMBLY WITH PLURAL ROTORS 审中-公开

    公开(公告)号：EP4015365A1

    公开(公告)日：2022-06-22

    申请号：EP21215617.8

    申请日：2021-12-17

    申请人： Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company

    发明人： THOMAS, Jason Hunter ,  BUTT, Lauren Marie ,  STARUK, William Joseph

    IPC分类号： B64C11/50 ,  B64C11/48 ,  B64C11/46 ,  B64C29/00

    摘要： An aircraft rotor assembly (12) comprises first and second rotors (42A, 42B) and a drive assembly (46). The first and second rotors are rotatable about a common axis (A) synchronously and with respect to each other. The first rotor has a first blade (44A) extending radially from the common axis; the second rotor has a second blade (44B) extending radially from the common axis, longitudinally offset from the first blade along the common axis. The drive assembly is coupled to the first and second rotors and configured to controllably vary, during continuous rotation of the first and second rotors, a differential phase angle (φ) separating the first and second blades as projected onto a plane (P A , P B ) perpendicular to the common axis.

    SINGLE LEVER CONTROL IN TWIN TURBOPROPELLER AIRCRAFT
    18.
    发明公开
    SINGLE LEVER CONTROL IN TWIN TURBOPROPELLER AIRCRAFT 审中-公开

    公开(公告)号：EP3366591A1

    公开(公告)日：2018-08-29

    申请号：EP18157799.0

    申请日：2018-02-21

    申请人： Pratt & Whitney Canada Corp.

    发明人： LISIO, Carmine

    IPC分类号： B64D31/12 ,  B64C11/50 ,  B64C11/30

    CPC分类号： B64C11/50 ,  B64C11/305 ,  B64D31/00 ,  B64D31/12

    摘要： Herein provided are methods and systems for controlling operation of a first propeller (120) of an aircraft, the first propeller (120) associated with a first engine (110), the aircraft further comprising a second propeller (170) associated with a second engine (160). A first requested engine power for the first engine (110) is obtained. A second requested engine power for the second engine (160) is obtained. The first propeller (120) is synchronized with the second propeller (170) by setting a first propeller command for the first propeller (120) based on the first and second requested engine power, and the first propeller command is sent for the first propeller (120).

    Verfahren zur Regelung von Fluggasturbinen
    20.
    发明公开
    Verfahren zur Regelung von Fluggasturbinen 有权

    公开(公告)号：EP1215383A1

    公开(公告)日：2002-06-19

    申请号：EP01127850.4

    申请日：2001-11-22

    申请人： Rolls-Royce Deutschland Ltd & Co KG

    发明人： Stephan, Volker

    IPC分类号： F02C9/42 ,  B64C11/50 ,  B64D31/12

    CPC分类号： F02C9/42 ,  B64C11/50 ,  B64D31/12 ,  Y02T50/671

    摘要： Die Erfindung betrifft den Austausch, die Entnahme bzw. das Hinzufügen von Medien und/oder Leistung zwischen den verschiedenen Wellen eines Triebwerks, zwischen verschiedenen Triebwerken und den Triebwerken mit dem Flugzeug. Hierdurch ergeben sich erfindungsgemäß zusätzliche Freiheitsgrade zum Erzielen von Triebwerksparametern, um die negativen Resonanzen oder Schwebungen zu verringern oder zu vermeiden.

    摘要翻译： 用于调节配备有至少两个动力单元的飞机的动力单元的方法包括从至少一个动力单元抽取能量，向至少一个动力单元添加能量，从至少一个动力单元移除流体， 一个动力单元，或从至少一个动力单元去除燃料空气。 首选功能：至少一个动力单元的旋转改变。 电力和液压能量被添加和/或移除。